CN106122349A - A kind of fluid damping mechanism of buffer unit - Google Patents
A kind of fluid damping mechanism of buffer unit Download PDFInfo
- Publication number
- CN106122349A CN106122349A CN201610709430.XA CN201610709430A CN106122349A CN 106122349 A CN106122349 A CN 106122349A CN 201610709430 A CN201610709430 A CN 201610709430A CN 106122349 A CN106122349 A CN 106122349A
- Authority
- CN
- China
- Prior art keywords
- baffle ring
- oilhole
- buffer unit
- spindle
- damping mechanism
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/32—Details
- F16F9/34—Special valve constructions; Shape or construction of throttling passages
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/60—Oleo legs
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Damping Devices (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses the fluid damping mechanism of a kind of buffer unit.The fluid damping mechanism of described buffer unit includes spindle and oilhole baffle ring；Described spindle includes that main body is up-small and down-big variable section structure and bottom is spherical structure；It is the cross section formed after polygon rounding that described variable section structure is perpendicular to the cross section of spindle length direction, and the camber line of all fillet sections of a certain cross section extend after form a circle；Described oilhole baffle ring coordinates with the upper gap of described spindle.Present invention stability during in use main oil-hole discharge coefficient stably ensure that aircraft landing also improves the comfortableness in landing mission.
Description
Technical field
The present invention relates to the fluid damping mechanism of a kind of buffer unit, belong to aircraft system field of structural design.
Background technology
Current big-and-middle-sized carrier undercarriage buffer unit is generally adopted by constant cross-section spindle or circular platform type oil
Pin, oilhole baffle ring is all fixed structure, rises as Chinese patent CN201010586712.8 discloses a kind of potential energy storage type projection
Fall frame buffer, belongs to undercarriage buffer.Including urceolus, piston rod, center oilhole eyelid retractor, depression bar and stopping means.
More than above-mentioned intermediate support surfaces until constituting between urceolus top and controlling chamber；Fluid top constitutes low pressure between intermediate support surfaces
Air cavity；The piston rod outer barrel and the top that are positioned at high pressure chest floating piston top constitute main oil pocket；Outside annular piston, piston rod
Annular projection oil pocket is constituted between cylinder lateral wall and outer tube inner wall；Constitute between bottom high pressure chest floating piston and piston rod urceolus
High pressure air cavity；This buffer has that the projection time is short, and projection is effective, is easily controlled, the feature of simple in construction, and can be used for short
Away from the land airplane taken off.
But, the main oil-hole face that the fluid damping mechanism of above-mentioned constant cross-section spindle and fixed oilhole baffle ring composition is formed
Long-pending the most constant, along with maneuvering load is gradually increased, oilhole discharge coefficient is unstable.Circular platform type spindle and fixed
The fluid damping mechanism of oilhole baffle ring composition in use may cause spindle to use the longevity due to the irregular impact of fluid
Life is substantially reduced, and spindle once ruptures, and during aircraft landing, the ineffective consequence of undercarriage is hardly imaginable.
Summary of the invention
It is desirable to provide the fluid damping mechanism of a kind of buffer unit, this fluid damping mechanism can guarantee that main oil-hole stream
Coefficient of discharge is stable, extend the service life of spindle.
To achieve these goals, the technical solution adopted in the present invention is:
The fluid damping mechanism of a kind of buffer unit, including spindle and oilhole baffle ring；It is structurally characterized in that, described spindle includes main
Body is up-small and down-big variable section structure and bottom is spherical structure；Described variable section structure is perpendicular to the horizontal stroke of spindle length direction
Cross section is the cross section formed after polygon rounding, and the camber line of all fillet sections of a certain cross section extend after form one
Circle；Described oilhole baffle ring coordinates with the upper gap of described spindle.
Thus, this cross section can ensure that spindle deflects when contacting with baffle ring not shadow under Oil shocking effect effectively
Rang pasta to amass, meanwhile, bottom hemispheric structure make spindle energy Small-angle Rotation ensure spindle does not haves a clamping stagnation, thus using
During main oil-hole discharge coefficient stably ensure that the stability during aircraft landing and improve in landing mission comfortable
Property.
According to embodiments of the invention, it is also possible to the present invention is further optimized, below for the skill formed after optimizing
Art scheme:
Preferably, described variable section structure is perpendicular to the cross section of spindle length direction is the cross section formed after square rounding.
The internal diameter of described oilhole baffle ring is joined with the consistent gap of circumscribed circle diameter of a certain cross section of described variable section structure
Close.
Preferably, the circumscribed circle diameter of each cross section of described variable section structure is equal.
Described oilhole baffle ring be can multiple degrees of freedom moves in buffer unit floating type baffle ring, thus, oilhole baffle ring is adopted
With floating type, can effectively prevent in use spindle stress the most by bending from improving service life.
Preferably, described buffer unit includes the plunger with hollow channel, the base being fixed in plunger and block；Institute
State the installing space forming oilhole baffle ring between base and block, and have between the sidewall of oilhole baffle ring and base between radial direction
Gap.Thus, first spindle contacts with oilhole baffle ring in Oil shocking effect, is then arranged in radial clearance with oilhole baffle ring
Oleo cushion, it is to avoid traditional spindle and baffle ring rigid contact and cause the situation of looper.
In order to ensure that oilhole baffle ring obtains buffering when receiving impact in radial direction, described base has installation oilhole
It is provided with radial clearance between the mounting groove of baffle ring, and the mounting groove sidewall of the sidewall of oilhole baffle ring and base.
In order to ensure that oilhole baffle ring obtains buffering when receiving impact at axial direction, described block is towards the end face of base
On have dashpot, be provided with axial gap between bottom land and the end face of oilhole baffle ring of this dashpot.
Compared with prior art, the invention has the beneficial effects as follows: the main oil-hole discharge coefficient that fluid damping mechanism is formed is steady
Fixed, spindle high life.
Accompanying drawing explanation
Fig. 1 is constant cross-section spindle and the fluid damping mechanism schematic diagram of fixed oilhole baffle ring composition.
Fig. 2 is circular platform type spindle and the fluid damping mechanism schematic diagram of fixed oilhole baffle ring composition.
Fig. 3 is the structure principle chart of one embodiment of the invention；
Fig. 4 is spindle schematic cross-section of the present invention；
Fig. 5 is the Section A-A figure of Fig. 4；
Fig. 6 is the section B-B figure of Fig. 4.
In the drawings
1-spindle；2-oilhole baffle ring；3-plunger；4-fluid；5-base；6-block；The circumscribed circle diameter of a certain cross section of X-；Y,
The width of a certain cross section of Z-spindle.
Detailed description of the invention
Below with reference to accompanying drawing and describe the present invention in detail in conjunction with the embodiments.It should be noted that in the feelings do not conflicted
Under condition, the embodiment in the present invention and the feature in embodiment can be mutually combined.For sake of convenience, hereinafter as occurred
On " ", D score, "left", "right" printed words, only represent consistent with the direction, upper and lower, left and right of accompanying drawing itself, structure is not played limit
It is set for using.
The fluid damping mechanism of a kind of buffer unit, sees accompanying drawing 3, Fig. 4, novel fluid damping mechanism, it be one by
Rounded square variable cross-section spindle and the mechanism of relocatable oilhole baffle ring composition, the main body of spindle is by rounded square multi-section shape
The entity become, the bottom of spindle is spherical structure.Oilhole baffle ring can move by multiple degrees of freedom in buffer unit.
As shown in Figure 3 oilhole baffle ring is designed to the structure of multifreedom motion in buffer unit, baffle ring internal diameter
Matched in clearance in the same size with spindle external diameter.
If the cushion stroke of undercarriage buffer unit is 160mm, calculating stroke by shock-absorbing capacity software for calculation is
Main oil-hole fluid when 40mm, 80mm, 120mm, 160mm passes through area, such that it is able to calculate the spindle of each travel point
Area of section, thus design the rounded square cross section of each travel point of spindle, as shown in Figure 4, spindle is to be passed through mutually by multi-section
The entity formed and spherical bottom are formed.
Described buffer unit includes the plunger 3 with hollow channel, the base 5 being fixed in plunger 3 and block 6.Described
Oilhole baffle ring 2 gap is arranged between base 5 and block 6.The mounting groove installing oilhole baffle ring 2, and oil is had on described base 5
It is provided with radial clearance between sidewall and the mounting groove sidewall of base 5 of hole baffle ring 2.Described block 6 is opened on the end face of base 5
There is dashpot, between bottom land and the end face of oilhole baffle ring 2 of this dashpot, be provided with axial gap.Thus, the oilhole gear of the present invention
Ring uses floating type, can effectively prevent in use spindle stress the most by bending from improving service life, and spindle uses circle
Angle square variable-section structure and spherical bottom structure, this feature can guarantee that spindle deflects under Oil shocking effect and connects with baffle ring
Not affecting pasta time tactile to amass and clamping stagnation, the fluid damping mechanism that spindle and floating type oilhole baffle ring structure form is in the process of use
Middle main oil-hole discharge coefficient stably ensure that the stability during aircraft landing the comfortableness that improve in landing mission.
The content that above-described embodiment illustrates should be understood to that these embodiments are only used for being illustrated more clearly that the present invention, and not
For limiting the scope of the present invention, after having read the present invention, the those skilled in the art's various equivalent form of values to the present invention
Amendment each fall within the application claims limited range.
Claims (8)
1. a fluid damping mechanism for buffer unit, including spindle (1) and oilhole baffle ring (2)；It is characterized in that, described spindle
(1) include that main body is up-small and down-big variable section structure and bottom is spherical structure；Described variable section structure is perpendicular to spindle (1)
The cross section of length direction is the cross section formed after polygon rounding, and the camber line of all fillet sections of a certain cross section extends
One circle of rear formation；Described oilhole baffle ring (2) coordinates with the upper gap of described spindle (1).
The fluid damping mechanism of buffer unit the most according to claim 1, it is characterised in that described variable section structure is vertical
The cross section formed after the cross section of spindle (1) length direction is square rounding.
The fluid damping mechanism of buffer unit the most according to claim 1, it is characterised in that described oilhole baffle ring (2)
The consistent matched in clearance of circumscribed circle diameter of internal diameter and a certain cross section of described variable section structure.
The fluid damping mechanism of buffer unit the most according to claim 3, it is characterised in that described variable section structure each
The circumscribed circle diameter of cross section is equal.
5. according to the fluid damping mechanism of the buffer unit one of claim 1-4 Suo Shu, it is characterised in that described oilhole baffle ring
(2) for can multiple degrees of freedom moves in buffer unit floating type baffle ring.
6. according to the fluid damping mechanism of the buffer unit one of claim 1-4 Suo Shu, it is characterised in that described buffer unit
Including having the plunger (3) of hollow channel, the base (5) being fixed in plunger (3) and block (6)；Described base (5) and block
(6) form the installing space of oilhole baffle ring (2) between, and have between the sidewall of oilhole baffle ring (2) and base (5) between radial direction
Gap.
The fluid damping mechanism of buffer unit the most according to claim 6, it is characterised in that described base has on (5)
The mounting groove of oilhole baffle ring (2) is installed, and is provided with between the mounting groove sidewall of the sidewall of oilhole baffle ring (2) and base (5) radially
Gap.
The fluid damping mechanism of buffer unit the most according to claim 7, it is characterised in that described block (6) is the end of towards
Have dashpot on the end face of seat (5), between bottom land and the end face of oilhole baffle ring (2) of this dashpot, be provided with axial gap.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610709430.XA CN106122349B (en) | 2016-08-23 | 2016-08-23 | A kind of fluid damping mechanism of buffer unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610709430.XA CN106122349B (en) | 2016-08-23 | 2016-08-23 | A kind of fluid damping mechanism of buffer unit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106122349A true CN106122349A (en) | 2016-11-16 |
| CN106122349B CN106122349B (en) | 2018-06-01 |
Family
ID=57275536
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610709430.XA Active CN106122349B (en) | 2016-08-23 | 2016-08-23 | A kind of fluid damping mechanism of buffer unit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106122349B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111473083A (en) * | 2020-04-21 | 2020-07-31 | 中国商用飞机有限责任公司 | Damping device |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS57134033A (en) * | 1981-02-13 | 1982-08-19 | Showa Mfg Co Ltd | Hydraulic buffer |
| JP2005090606A (en) * | 2003-09-16 | 2005-04-07 | Showa Corp | Friction giving structure of hydraulic buffer |
| CN102094926A (en) * | 2010-12-14 | 2011-06-15 | 南京航空航天大学 | Potential energy storage type protruding undercarriage buffer |
| CN102338186A (en) * | 2011-09-02 | 2012-02-01 | 北京航空航天大学 | Conical damping hole type buffer for undercarriage of passenger plane |
| CN203285899U (en) * | 2013-05-30 | 2013-11-13 | 江西洪都航空工业集团有限责任公司 | Variable oilhole structure of undercarriage buffer |
| CN103629290A (en) * | 2013-11-27 | 2014-03-12 | 中国航空工业集团公司西安飞机设计研究所 | Variable damping oil needle of airplane buffer |
| CN203892441U (en) * | 2014-04-17 | 2014-10-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Oil needle and landing gear buffer with oil needle |
-
2016
- 2016-08-23 CN CN201610709430.XA patent/CN106122349B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS57134033A (en) * | 1981-02-13 | 1982-08-19 | Showa Mfg Co Ltd | Hydraulic buffer |
| JP2005090606A (en) * | 2003-09-16 | 2005-04-07 | Showa Corp | Friction giving structure of hydraulic buffer |
| CN102094926A (en) * | 2010-12-14 | 2011-06-15 | 南京航空航天大学 | Potential energy storage type protruding undercarriage buffer |
| CN102338186A (en) * | 2011-09-02 | 2012-02-01 | 北京航空航天大学 | Conical damping hole type buffer for undercarriage of passenger plane |
| CN203285899U (en) * | 2013-05-30 | 2013-11-13 | 江西洪都航空工业集团有限责任公司 | Variable oilhole structure of undercarriage buffer |
| CN103629290A (en) * | 2013-11-27 | 2014-03-12 | 中国航空工业集团公司西安飞机设计研究所 | Variable damping oil needle of airplane buffer |
| CN203892441U (en) * | 2014-04-17 | 2014-10-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Oil needle and landing gear buffer with oil needle |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111473083A (en) * | 2020-04-21 | 2020-07-31 | 中国商用飞机有限责任公司 | Damping device |
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| Publication number | Publication date |
|---|---|
| CN106122349B (en) | 2018-06-01 |
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